Aircraft, missile, projectile or underwater vehicle with reconfigurable control surfaces and method of reconfiguring

Abstract

The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and a method for increasing the maneuverability or stability of an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to a method for increasing the maneuverability or stability of an aircraft, missile, underwater vehicle or projectile through the use of removable control surfaces. The technical advantage of the removable control surface system (or removable control surface) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.

Claims

1. A method of increasing the maneuverability or increasing the stability of an aircraft, missile, underwater vehicle, or projectile comprising steps of: causing an aircraft, missile, underwater vehicle, or projectile to move, take off, launch, or otherwise be released into a designed path of travel, the aircraft, missile, underwater vehicle, or projectile having a center of pressure and comprising a body, at least one control surface having an area, and a sensor or device for detecting changes in condition; detecting with the sensor or device a change in condition requiring increased maneuverability or increased stability; outputting from the sensor or device a signal indicating the change of condition detected; and causing the area of the at least one control surface to be varied to increase maneuverability or increase stability by changing the center of pressure of the aircraft, missile, underwater vehicle or projectile based at least in part on the signal of the sensor or device, wherein the sensor or device is a GPS, radar or an infra-red device.

2. The method of claim 1 wherein part of the at least one control surface is varied by exploding a releasable connector which connects the part of the at least one control surface to the rest of the control surface, releasing a clamp which holds the part of the at least one control surface to the rest of the control surface, removing a hinge which connects the part of the at least one control surface to the rest of the control surface, or exploding a bolt which connects the part of the at least one control surface to the rest of the control surface.

3. The method of claim 1 wherein the aircraft, missile, underwater vehicle or projectile comprises at least two control surfaces, wherein multiple removable control surfaces, when attached, form one control surface of the at least two control surfaces, and wherein the multiple removable control surfaces provide multiple states of stability.

4. The method of claim 1 where the sensor or device transmits a signal to a controller via a satellite.

5. A method of increasing the maneuverability or increasing the stability of an aircraft, missile, underwater vehicle, or projectile comprising steps of: causing an aircraft, missile, underwater vehicle, or projectile to move, take off, launch, or otherwise be released into a designed path of travel, the aircraft, missile, underwater vehicle, or projectile having a center of pressure comprising a body, at least one control surface having an area, at least one sensor or device for detecting changes in condition, the at least one sensor or device having a signal, and a closed-loop control system; causing with the closed-loop control system the area of the at least one control surface to be varied based on the signal of the at least one sensor or device to increase maneuverability or increase stability by changing the center of pressure of the aircraft, missile, underwater vehicle or projectile, wherein part or all of the at least one control surface is varied by exploding a releasable connector which connects the part of the at least one control surface to the rest of the control surface, releasing a clamp which holds the part of the at least one control surface to the rest of the control surface, removing a hinge which connects the part of the at least one control surface to the rest of the control surface, or exploding a bolt which connects the part of the at least one control surface to the rest of the control surface.

6. The method of claim 5 wherein the aircraft, missile, underwater vehicle, or projectile comprises at least two control surfaces used to change the center of pressure of the aircraft, missile, underwater vehicle or projectile.

7. A method of increasing the maneuverability or increasing the stability of an aircraft, missile, underwater vehicle or projectile during travel comprising the steps of: causing an aircraft, missile, underwater vehicle or projectile to move, take off, launch or otherwise be released into a designed path of travel, the aircraft, missile, underwater vehicle or projectile comprising a body, at least one control surface having an area, a sensor or device for detecting changes in condition, the sensor or device having a signal, and a closed-loop control system; causing with the closed-loop control system the area of the at least one control surface to be removed or reduced during travel in response in part to the signal from the sensor or device to increase maneuverability or increase stability.

8. The method of claim 7 wherein the aircraft, missile, underwater vehicle, or projectile comprises at least two control surfaces.

9. The method of claim 7 wherein the sensor or device outputs the signal to the closed-loop control system which increases or decreases the area of the at least one control surface during travel based at least in part on the signal of the sensor or device.

10. The missile or projectile of claim 9 wherein the closed loop control system is a proportional-integral-derivative controller, an adaptive predictive controller or an adaptive predictive feedback controller.

11. The missile or projectile of claim 9 wherein the device or sensor is an infra-red sensor.

12. The missile or projectile of claim 9 wherein the device or sensor is a radar.

13. The missile or projectile of claim 9 wherein the device or sensor is a GPS device.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1. Isometric view of one embodiment of a missile having a number of control surfaces.

(2) FIG. 2. Isometric view of one embodiment of an underwater vehicle having a number of control surfaces.

(3) FIG. 3. Isometric view of one embodiment of the aft body of a missile with removable fins.

(4) FIG. 4. Cutaway isometric view of the embodiment in FIG. 3 of the aft body of a missile having a number of removable fins that have been removed.

(5) FIG. 5. Cross sectional partial cutaway of an aircraft vertical stabilizer with attached removable control surface. The removable control surface is attached to the vertical stabilizer with two exploding bolts.

(6) FIG. 6. Isometric view of the tip of an aircraft wing or missile fin with a removable trailing edge. The trailing edge is connected to the wing or fin by two bolts.

(7) FIG. 7. Schematic view of various stages of a missile fired from an aircraft to intercept and destroy an incoming missile, showing the removable control surfaces being removed during flight.

(8) FIG. 8. Schematic flow diagram of removable control surfaces for aircraft, missiles, projectiles, or underwater vehicles of the present invention.

(9) FIG. 9. Flow diagram illustrating method embodiments.

DESCRIPTION OF THE PREFERRED EMBODIMENT(S)

(10) The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and to an improved control system for maneuvering an aircraft, missile, projectile or underwater vehicle. More particularly the present invention relates to these aircraft, missiles, projectiles or underwater vehicles with removable and variable control surfaces for adaptively modifying stability. More particularly, the present invention relates to an aircraft, missile, underwater vehicle or projectile with removable control surfaces which also affects maneuvering performance, in-flight.

(11) The aircraft, missile, projectile, or underwater vehicle of the present invention can be any one of those devices with the improved control system described in this application. Underwater vehicles include, but are not limited to torpedoes and submarines. Projectiles include but are not limited to large caliber bullets, shells, bombs and bomblets. The control system, alone or as part of the aircrafts, missiles, under water vehicles or projectiles described in various other embodiments of the present invention, preferably allows the user of these vehicles or devices to change their center of pressure of the device in flight or in the case of an underwater vehicle such as a torpedo or submarine, after firing or during operations respectively.

(12) The vehicle comprises a body and at least one control surface, wherein all or part of the at least one surface is removable. The removable control surface being removable in flight, after launching or during operation. The removable control surface of the present invention comprises at least one removable control surface, a mechanism for attaching the at least one removable control surface to another surface and at least one non-removable surface or for attaching the removable control surface. Preferably the control systems of the various embodiments of the present invention contain a number of removable control surfaces which will improve the versatility and maneuverability of the aircraft, missile, projectile, or underwater vehicle upon which the control system is preferably used. Still preferably, the control system contains at least two control surfaces with accompanying connection mechanisms or connectors. More preferably, the control system contains at least three removable control surfaces with accompanying connection mechanisms or connectors. Still more preferably, the control system contains at least four control surfaces with accompanying connection mechanisms or connectors. Most preferably, the control system contains at least six control surfaces with accompanying connection mechanisms or connectors. In various embodiments of the present invention multiple control surfaces can connect using a single or multiple connection mechanism(s) or connector(s).

(13) The control surfaces and removable control surfaces of the present invention are any surface attached to the aircraft, missile, projectile, or underwater vehicle, which affects the center of pressure of the device. Examples include, but are not limited to wings, fins, stabilizers and control planes specifically for underwater vehicles.

(14) The connection mechanism or connector of the present invention connects the removable control surface to a connection surface. The connection surface can be either the body of the aircraft, missile, projectile or underwater vehicle, a non-removable control surface or another removable control surface. Connection mechanisms or connectors can include, but are not limited to adhesives, exploding bolts, mechanical weaknesses, clamps, hinges, screws, magnets, etc. The connection mechanism or connectors must be able to securely fasten the removable control surface to a connection surface and detach the removable control surface when directed to by the control system or by the user. Activating the connection mechanisms or connectors may be accomplished by a number of mean, each according to the specific type of connection mechanism or connectors. Electrical motors, pneumatics or hydraulics may be used to activate clamps, hinges or screws or an electrical charge can activate exploding bolts or magnets. Any number of connection mechanisms or connectors may be used to connect the removable control surface to the connection surface. The number and placement of connection mechanisms may vary from one mechanism at one point along the connection surface to multiple connection mechanisms at multiple points along the connection surface. The number, type and configuration of connection mechanisms or connectors and the manner in which they are released will vary depending on the specific application and will be apparent to those skilled in the art. Once the removable control surfaces have been released, they will be pulled away from the body of the aircraft, missile, projectile or underwater vehicle by the drag of the fluid through which they are moving, e.g. air or water.

(15) One embodiment of the present invention will have multiple removable control surfaces, that when attached, form one control surface. Each removable control surface preferably is individually addressable and can be removed at separate times in flight, after firing or during operation. Alternatively, multiple control surfaces may be released by activating one or a set of connection mechanisms. Multiple removable control surfaces provide the aircraft, missile, projectile or underwater vehicle with multiple states of stability. The multiple removable control surfaces can be also configured so that they are forward and aft of each other, medially and laterally of each other or any other positioning specific to the desired application.

(16) The connection mechanisms are preferably activated by an onboard control system. The control system can be for example a proportional-integral-derivative (PID) controller, an adaptive predictive controller, an adaptive predictive feedback controller or another computer-controller. The controller of the present invention is preferably a closed loop control system. The system monitors parameters from sensor or other devices outputs and analyzes the data to determine whether any changes to the stability of the aircraft, missile, underwater vehicle or projectile need to be made. Sensors or other devices can be located onboard or located remotely. Devices can include, but are not limited to GPS, radar, altimeter, barometer, IR, RF, and transmitter beacons. Sensors can include, but are not limited position, speed, distance, airflow and pressure. The output of these sensors or other devices are used to determine when, which and what number of connection mechanisms must be actuated thus allowing the specified control surfaces to be removed.

(17) The sensor or device transmits a signal to the controller through either an electrical connection or by a wireless communication (e.g. IR, RF, satellite, etc.) Multiple sensors and/or devices send multiple signals to the controller or multiple controllers. The controller(s) processes the signal(s) to determine, through mathematical modeling, the dynamics of the aircraft, missile, projectile, or underwater vehicle. It is the predictive ability of the controller, which expands this system from being merely responsive to being predictive. This is especially advantageous for dynamic systems, which are nonlinear and time varying and operating in dynamic environments. The controller is preferably a computer or microprocessor. The controller produces an output signal to an actuator, monitor, recorder, alarm and/or any peripheral device for alarming, monitoring, or in some manner, affecting or more rapidly adjusting the dynamics upon its incipience. Preferably, the output of the controller is used to activate the connection mechanisms used to release the removable control surfaces. Advantageously, the controller is the ORICA controller, an extended horizon, adaptive, predictive controller produced by Orbital Research Inc. and patented under U.S. Pat. No. 5,424,942, which is incorporated herein by reference. Under certain conditions, the controller (or optionally an external controller) which is preferably connected via electrical or hydraulic connection to the connection mechanisms, causes the connection mechanisms to activate, releasing the removable control surfaces. The control system can also be a partially closed loop control system, which accepts input from not only the sensor(s) or device(s), but from other systems as well and additionally human input.

(18) FIG. 1 is an isometric view of one embodiment of a missile 12 having a number of control surfaces 15. In FIG. 1, the missile 12 has fins 14 on its forebody 13 and aftbody 16. Depending on this missile's 12 configuration either or both the fins 14 on the forebody 13 and aftbody 16, or portions thereof, being removable (not shown).

(19) FIG. 2 is an isometric view of one embodiment of a torpedo 22 having a number of control surfaces 23 on its aft body 21. In FIG. 2, the torpedo 22 has four fins 24 (one not shown) on its aft body 21 along with a propeller 20 for driving the torpedo 22. At least one of the torpedo fins 24 or control surfaces 23 being removable (not shown).

(20) FIG. 3 is an isometric view of one embodiment of a missile 30 having four fins 31 on its forebody 32 and four fins 33 on its aftbody 34. The fins 33 on the missile's aftbody 34 contain removable control surfaces 35 on their trailing edge 36. These fins 33 have a mechanical weakness 34 built into the fins 33, which functions as the connecting mechanism or connector 34. This mechanical weakness 34 allows the fins to be detached using small controlled explosives (not shown) to detach the removable portion of the fin 35. These small controlled explosives are actuated by either a controller or by human intervention.

(21) FIG. 4 is a cutaway isometric view of the aft portion 40 of a missile 41. In FIG. 4, the four aft fins 42 are shown with their respective removable control surfaces 43 detached. The four arrows 44 illustrate the direction and movement of the removable control surfaces 43 once they are detached from the aft fins 42.

(22) FIG. 5 is a cross sectional partial cutaway of an aircraft's stabilizer 51 with attached removable control surface 50. The removable control surface 50 is attached to the stabilizer 51 by exploding bolts 52. When the aircraft's pilot (not shown) or controller (not shown) determines a need for a change in stability is necessary, it sends an electric charge to the exploding bolts 52. The electric charge causes the exploding bolts 52 to detonate 53. The detonation 53 severs the connection between the stabilizer 51 and removable control surface 50 and allows the removable control surface 50 to detach. This alters the center of pressure towards the front of the aircraft and increases the maneuverability.

(23) FIG. 6 is a transparent isometric view of the tip of an aircraft wing or missile's fin 60 with a removable trailing edge 61. The trailing edge 61 is connected to the wing or fin 60 by two bolts 62. The bolts 62 are unscrewed from either the wing or fin 60 or the trailing edge 61 to release the trailing edge 61. Pneumatics, electrical motors or hydraulics (not shown) can be used to unscrew the bolts 62. The bolts 62 are preferably released from the wing or fin 60 and remain attached to the trailing edge 61 when released.

(24) FIG. 7 is a schematic view of various stages of a missile 71 fired from an aircraft 70 to intercept 79 and destroy an incoming missile 72, showing the removable control surfaces 73 being removed during flight. In FIG. 7, a missile 71 is fired from an aircraft 70. When fired, the missile 71 has the removable control surfaces 73 attached to the rear sections of the missile's 71 rear fins 74. The missile 71 is fired from the aircraft's 70 underbody (not shown). The missile's 71 flight can be broken up into three stages. The first flight stage is missile launch 75. Missile launch 75 subjects the missile 71 to high cross-winds which require the missile 71 to have full control surfaces 73 for stability. The second flight stage is approach 76. During the approach stage the missile 71 flies towards the incoming missile 72. Approach 76 is characterized by fairly straight flight requiring stability, but not as much as launch 75. The approach 76 distance may vary greatly from many miles down to feet and in certain situations, may not be present. The third and final flight stage is interception 77. During the interception 77 stage the missile 71 requires great maneuverability to intercept 79 the incoming missile 72. The removable control surfaces 73 are shed to permit the missile 71 increased maneuverability. The missile's 71 final configuration 78 is minus the removable control surfaces. The interception stage 77 is characterized by multiple, sharp maneuvers.

(25) FIG. 8 is a schematic flow diagram of removable control surfaces for aircraft, missile, underwater vehicles or projectiles of the present invention. In FIG. 8, a controller 82 accepts input from a monitoring device 86 or sensor 88, other data from various sources and/or human input 92. The controller 82 based at least in part on the input from a monitoring device 86 or a sensor 88 actuates a device 94 to remove the removable control surface. This actuator for example can be a motor 96 or hydraulics 98, which causes this movement.

(26) FIG. 9 illustrates methods of increasing the maneuverability or increasing the stability of an aircraft, missile, underwater vehicle or projectile during travel according to various embodiments of the present invention. In one embodiment, an aircraft, missile, underwater vehicle or projectile moves, takes off, launches, or is otherwise released into a designed path of travel 91. Next, a sensor or device on the aircraft, missile, underwater vehicle or projectile detects a change in a condition 93. The signal from the sensor or device is sent to a closed-loop control system which causes the area of a control surface to be removed or reduced during travel in response in part to a signal from the sensor or device 95. The closed-loop control system may also increase or decrease the area of a control surface during travel based at least in part on a signal from the sensor or device 97. As a result of the action by the closed-loop control system, the configuration of the aircraft, missile, underwater vehicle or projectile is modified in-flight, the relative positions of the center of pressure and center of gravity are altered, and thus either maneuverability or stability is increased 99.